Internal-combustion engine of the turbine type.



l l VMTENT-HDSLN:17', V1907. H. P. PULLAGAR al' J. F. BOTTOMLEY. INTERNAL GoMBUsTIoN 'ENGINE 0F THE TURBINB TYPE.

IPLIUATION FILED IV. 30, 1908.

No. 866,352. Y PATBNTBD sum1?, 1907.

\ 11.1". FULLAGAM J. E. BOTTOMLEY. K INTERNALGOMBUSTIONENGINE '0F THB TURBINB TYPE.

APPLICATION FILED NOV. 30, 190?. l

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'No'. 866,352. l NNTNNTNDsBPTfU,1907.*1 M

H.P.`PULLAGAN&.J.N.BOTTO'MLBY. INTERNAL coMBUsTIoN ENGINE oF TNB TURBINB TYPE.

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, UNITED STATES PATENT-OFFICE.

IIUGH FRANCIS FULLAGAR AND JAMES FRANCIS BOTTOMLEY, OF NEWGSTLE-UPON-TYNE, j

ENGLAND.

Specification of Letters Patent.'

Patented Sept. l1"?, 1907'.y

Application filed November 30, 1 906. Serial No. 3455823- To all whom it may concern:

13e it knownthat we, HUGH FRANers FULL/reas and .Linus FRANCIS .Bo'rToMLEY, subjects of the King of Great Britain and Ireland, residing, respectively, at Newcastle-upon-Tyne, in the county of 'Northumberland, England, have invented Improvements in Intermal-Combustion Engines of the Turbine Type, of which the following is a specification.

This invention relates to internal combustion engines of the type wherein the combustion products of air and fuel emerging from a chamber in which combustion takes place act upon amotor of the turbine type to produce useful work. In an engine of this type the nozzle or nozzles by which the gases enter the turbine must necessarily be exposed to a very high temperature, while the temperature along the whole path or paths of the gases throughout the turbine will almost inevitably be also very high. Great difficulty has in consequence been experienced in constructing such turbines to resist the destructive action of the gases at such high temperatures, and to prevent the corrosion and distortion of the parts, under the intense heat, causing leakage and inisdirection of the gases and otherwise mpairing the efliciencyof the turbine.

It has already been proposed to line the parts subject to the highest temperatures with refractory materials but very great difficulties have been encountered because, as is well knowm the materials suitable for the purpose are all brittle and very liable to be cracked by mechanical strain, and because, especially in large turbines, the pressure on `these linings, due to the thrust of the gases, is considerable, and, owing to the large size and great length of such passages in'turbines of any practicable size, for example of 1000 horse power and upwards, a small difference in the coeicients of expansion between the refractory material and the casing causes severe strain. The best refractory material.

for maintaining a good surface, namely, fused silica, gives rise to the greatest difficulties, as its coefficient of expansion is practically nil.

Moreover, though it is possible to protect the rotat- 4' ing rings of turbine blades (which are `only intermittently subject to thehhot gases) by artificially cooling them, lthis method is not feasible in the caseof fixed blades and-passages continuously exposed to the hot gases, while even if such cooling were feasible, it would be highly undesirable, owing to the serious loss of heat and consequently of efficiency, which would be entailed. v

Now this invention has for its object to avoid the waste and corrosion of the surfaces exposed to the hot gases, to reduce as far as possible the area of such surfaces so as to reduce the loss of heat transmitted by them, and to prevent such heat as is unavoidably transmitted through them from reaching thecasings,

bearings and other parts of the turbine, and also to provide a construction in which the alinement and relative positions of the parts shall "be comparatively unaffected by high temperature or wide variations of tcmperature, so that leakage around the rotating'turbine 'blades shall be reduced and the efficiency of the motor maintained. For this purpose, the products of eom. bustion on leaving the combustion chamber are led to a passage of considerable length, the linings or walls of which are formed of fused silica or other refractory noncorrosive and practically non-conducting and non-expanding material firmly held in a metal frame or casing kept cool by water jacketing orother means, so that the temperatures of the metal casing and the walls are kept approximately at temperatures inversely proportional totheir coefficients of expansion, and that thc products of the large coeicient of the metal by its low temperature, and of the small coeicient of the walls by their high temperature are approximatelyy equal. In this way differences of expansion, such as would otherwise disturb the alinement and rigidity of the whole, are avoided.

The shape of thel passage is preferably such that the perimeter of cross section is small compared with the cross-sectional area so that the exposed surface is thereby limited. lhe passage is provided at .intervals with v blades are sufficiently far apart to allow this direction of the gases to be effected entirely'by the curvature of the passage itself. One or more guiding stationary blades, of a similar material, may be inserted lengthwise in the passage so as to subdivide the same in width and thereby enable it to be reduced in length, but, owing to the fact that the thin edgesand exposed surfaces of such blades are particularly liable to injury, the construction first mentioned is preferred. y

The linings or walls of the successive portions of the passage are preferably formed of fused silica or some suitable ceramic or vitreous material shaped to the re- 10( they are fitted,.with or withouta refractory non-'expand- 105 ing cement or packing material; in some cases the metallic frame or case maybe east around the material of the linings or walls. Such heat as would reach the casing through the refractory linings or walls is dissipated by a water jacket or other means so that the temv such heat as passes through the non-conducting lining is prevented/from reaching the other parts of the tur- .p bine. The passage as a whole will therefore not undergo such expansion or contraction as would disturb the clearance relations between the sides of the segmental notches or channels and the rotating rings of blades. f Itwill be understood that the quantity of heat to be absorbed and drawn off from the casing will depend 'inter alia upon the thickness and conductiality of the linings or Walls; 1

The rotating turbine blade wheels will of course be inclosed by a suitable casing, which may embrace, if desired, the case-or frame of'the gas passage hereinbefore described. The cooling of the latter has then the further advantage of intercepting such heat as passes through th'e non-conducting linings or`walls and prev enting it from reaching' the other parts of the turbine.

It is of course understood that the cross-sectional area of the passage at each point of its length is propon' tioned to the desired volume and velocity ofthe gases at that point, having regard to their temperature, the

drop of pressure to be effected, as well as the velocity to be extracted by each ring of rotating blades.V Owing to the low pressure and consequent low ratio of expansion advisable in internal combustion turbines, this accurate shapingof the passage throughout the whole of its length to produce the correct velocities, is a matter of far greater importance than in the case of steam turbines where a high pressure and therefore-a high ratiovof vexpansion is employed.

, cording to this invention may be combined in one turbine so as to direct hot gases on to the rotating rings of blades at more than one point simultaneously.

In the accompanying illustrative drawings, Figure 1 showsin longitudinal section on the linelA A of Fig. 2, Fig. 2 in end elevation,`and Fig. 3 in cross section on the line vB B of Fig. 1, one construction of internal combustion engine of the turbine type embodying the present invention. Fig. 4 is a developed longitudinal section rtaken through the gas passage on the line C C of Figs. 2 and 3. Fig. 5`is a similar view to Fig. 4 showing a modification. Fig. ,5l is a sectional view showing another modified construction. Figs. 6 and 7 are similar views to Figs. 1 and 4 respectively showing a further modification.

The engine shown in Figs. 1 to 4 inclusive is 'constructed withthree turbine wheels a mounted to rotate within a metal casing b and each provided with a single ring of blades c, the three wheels being fixed upon a rotary shaft d and connected together by tubular dise is a passage through which the highly heated combustion products are led from a combustion chamber (not shown) located at a lower level than the engine and caused to impinge upon the successive rings of turbine blades c. The said passage is formed of refractory non-corrosive and practically nonconducting and nonexpanding.rnaterial f, such as fused silica, which is firmly held within and surrounded by ametal frame or casing g with the several portions of the passage e in alinement with each other. The casing g is provided with a water jacket z through which cold water is caused to flow for" the purpose of keeping its tcmperature low and constant so as to avoid expansion and contraction and prevent such heat as reaches it from passing tothe remaining portion of the casing b to which the said casing gl is, as shown, fixed.

la are transverse segmental notches or channels cut at intervals in the material across the passage e into which the rings of turbine blades c extend so that the hot gases flowing through the said passage can act upon them. The passage is made of the curved form shown so as to direct the hot gases flowing through it, at the required angles against the successive rings ofblades c for rotating the same and the attached turbine wheels a. 'j e The gas passage e in the example shown,is of partly annular shape in cross section at-thel portions'where it meets the rings ofrevolving blades (see Figs. 2 and 3) thecross sectional area thereof at each point of its length from its inlet end el to its outlet end e2, being, as hereinbefore stated, proportioned to the vdesired volume and velocity of the gases at that point, having regard to the temperature of the gases, the drop in pressure to be effected, as well as the velocity to be extracted by each rotary ring of blades-c. For this purpose the part el of the passage leading from the combustion chamber to the first turbine -wheel a is made, vas shown for example at e* in Fig. 4, of a section which gradually contracts/towards the portion which forms the nozzle e3 by which the gases enter the turbine, after which it increases gradually and by steps as shown, towards the outlet end e2 which also mayadvantageoulsly be made of the flaring shape shown in Fig, 4, so as to reduce such velocity as re-` mains in the gases after passing through the last ring of rotating blades. The' proportions shown in the drawings are designed for a combustion pressure of 45 lbs. (forty five pounds) to the square inch absolute and a velocity at the rstring of rotating blades of about 3000 (three thousand.) feet per second. lt will be understood that for higher initial pressures, a greater' ratio of expansion must be provided for.

The sides of the notches or channels lc are accurately fitted to the rotating rings of blades c with the fine clearness desirable to prevent leakage of the gases.

Instead of making the Walls of the passage e whollyl of fused silica or equivalent rehactory material, as in the arrangement shown in Figs. l to 4, the said passage may, as shown in Fig. 5, be provided with linings f of such refractory material built up of plates or bricks secured to a more workable but 'good refractory nonexpanding material f2.' Inthis case the Water jacket h of the metal casing g in which the material f 2 is fixed, may, as shown, be made thicker so as to enable a greater volume of water to flow therethrough for carrying away the heat that passes through the said material.

Fig. 5 shows the nozzle portion of the gaspassage /with a modified form-of surrounding water jacket.

In the modified construction shown in Figs. 6 and 7, the transverse segmental notches or channels k are formed in and between inwardly extending' portions g oi the water jacketed casing g in order more iirml'y to hold the Walls or lining f or f l and to protect the edges thereof from becoming broken off. In other respects the modified constructions shown in Figs.- 5, 6 and 7 are similar to that shown in Figs. l to 4 inclusive. .l

m, mare apertures through which a-cooling fluid, for example water, can be admitted through the upper part oi the casingvb so as to come into contact. with the turbine blades vas 'the same rotate through this part o the casing4 and cool them. i

It wilLb'e evident that in cases where, owing to the pressures, or numberoi rings ot blades or the methods of cooling adopted, the temperature oi the 4gases towards'the exhaust endis so low as not to require the use of a refractory lining or wall to the passage, this vinvention need only be applied to the passages sub- Yjected to the higher temperatures.

What we claim isz- `1. In an internal combustion engine of the turbine type, a-tube or passage'of refractory and practically noncon ducting and non-expanding material through which highly heated products of combustion can flow at a great velocity, a metal frame or casing holding the parts of said tube or passage in correct alinement, and means for cooling said-frame or casing and maintaining the co-acting parts ab temperatures proportioned inversely to their coefllcients of expansion, substantially asdescrlbed for the purpose set forth.

2.-'In an internal combustion engine of the turbine type, a tube or passage of refractory and practically lnon-conducting and non-expanding material open at each end and throughlwhich highly heated products of combustion can ow at Va great velocity, and 'a frame or casing surrounding said tubeor passage and having a water jacket adapted vto maintain it at the required temperature relative to that of the refractory materlalinclosed thereby; substantially as described for the purpose set forth.

3. In an internal combustion engine of the turbine type, a tube or passage having its inner walls formed of-fused silica and open at each end for the flow of highly heated gases at a great veloctytherethrough, a metal frame or casing in which s aid tube or passage is firmly held with its parts in crrect alinement, and means for carrying away such heat as reaches said `trame or casing from said tube or passage. i

4. In an internal combustion engine of the turbine type, a tube or passage formed of refractory and .practically non-conducting and non-expanding material, the passageway therethrough being open at each end and reversely curved in the direction of its length, a metal trame or casing surrounding said tube or passage, and means for carrying away such heat as reaches said trame or casing from the tube or passage.

5. In an internal combustion engine of the turbine type, a tube or passage of refractory and practically non-conducting and nonfexpanding material through which highly heated products of combustion can continuously flow at a great velocity, tn1bine wheels extending into and across said tube orpassage, and a water jacketedframe or casing surrounding the Asaid material and arranged to support .the same on the sides thereof adjacent to the sides o! the wheels.

6. In hn internal combustion engine of the turbine type, blocks of Arefractory and practically non-conductingand non-expanding material arranged near together and having a reversely curved-passageway open at each end extending lengthwise therethrough for the flow of highly heated products of combustion at a great velocity, a water jacketed trame or casing surrounding said blocks and holding the same in correct alinement, and turbine wheels comprising a plurality of rotary rings of turbine blades extending transversely through said frame or casing and into said passageway.

blocks of refractory and practically nonconducting and .ing a reversely curved passageway open at each end extending lengthwise therethrough for the tlow of highly heated products of combustion at a great velocity, a water. jacketed frame or casing surrounding said blocks and holding the same in correct alinement, parts of said water -jacketedirame or casing extending between and so asrto .form portions of the side walls of transverse channels between said blocks, and turbine wheels comprising a plurality o`f rotary rings of turbine blades extending transversely through said 'frame or casing and channels and across said passageway.

8. In an internal combustion engine of the turbine type, the combination with'turbine wheels and a main inclosing casing of a substantially continuous tube or passage for the hot gases constructed of or lined with a refractory and practically non-expanding and non-conducting material and across which said turbine wheel extends, a frame or casing for iirmlyl holding the parts of said material in correct alinernent, and means for carrying away heat from said frame or casing and prevent it passing to the main casing and maintaining said frame or casing and tube or passage `at temperatures proportioned inversely to their co-eiicients of expansion.

9. In an internal combustion engine of the turblnetype, the combination with a plurality of rotary rings of turbine blades, and a main lnclosing casing, of a substantially continuous passage for the hot gases, said tube or passage being constructed of a refractory and practically non-corrosive non-conducting material with transversely arranged'segmental channels into which the rotary rings of blades extend, and being reversely curved in'the direction of its length to ydirect the hot gases at the required angles against the successive rings of blades, a frame or place with the successiye portions of the passage in corvrect alinement, and means for carryingv away such heat as reaches saidframe or casing from the refractory material.

10.. An internal combustion engine of the turbine type, comprising a plurality of rotary turbine wheels fixed upon a common shaft, a casing inclosing said turbine except at one side through which said wheels project, a -body of refractory nonvcorrosive and practically non-conducting and non-expanding material having a substantially continuous passageway extending lengthwise therethrough, and transverse segmental channels therein at intervals of its length into which said turbine wheels extend, a water jacketed metal frame or casing that surrounds and firmly holds said refractory material in place, fits into said main frame or casing, and through which said rotary turbine Wheels extend into the transverse channels and acrossthe passageway, the inlet end of said pgssage being made of a section that gradually contracts towards the portion which forms the nozzle by which the gases enter the turbine, and then increases in steps towards the outlet end of said passage, the intermediate portion of the passage being reversely curved in the dlrection of its length, substantially as described for the purpose specified.

Signed at Newcastle-on-Tyne, England, this nineteenth day of November 1906.

HUGH FRANCIS FULLAGAR. JAMES FRANCIS BOTTOMLEY.

Witnesses:

.Tous TnNNANT GRUNDY, Wrnmsn HAY.

non-expanding materialarranged near together and hav.

casing forrmly holding said non-conducting material ln- 7. Inan internal combustion engine of the. turbine type, Y

wheels 

